Blade track assembly, components, and methods

ABSTRACT

A blade track assembly is disclosed having a variety of features. The assembly can have annular or segmented components, or a combination of the two. In one form the assembly includes blade tracks having a forward and aft edge that can be received in an opening of respective hangers. The hangers can include anti-movement features to discourage movement of a blade track. A rib can extend between hangers and in one form can be used as part of a seal assembly. Clips can be used to secure the blade track in openings of the respective hangers, as well as to discourage movement of the blade track.

CROSS-REFERENCE TO RELATED APPLICATIONS

The present application claims the benefit of U.S. Provisional PatentApplication 61/582,275, filed Dec. 31, 2011, and is incorporated hereinby reference.

GOVERNMENT RIGHTS

The present application is a continuation of PCT Application No.PCT/US2012/072236, filed Dec. 30, 2012, which claims the benefit of U.S.Provisional Patent Application 61/582,275, filed Dec. 31, 2011, each ofwhich are incorporated herein by reference.

TECHNICAL FIELD

The present invention generally relates to turbomachinery components,and more particularly, but not exclusively, to gas turbine engine bladetracks.

BACKGROUND

Providing blade track arrangements for turbomachinery components, suchas for gas turbine engines, remains an area of interest. Some existingsystems have various shortcomings relative to certain applications.Accordingly, there remains a need for further contributions in this areaof technology.

SUMMARY

One embodiment of the present invention is a unique blade trackassembly. Other embodiments include apparatuses, systems, devices,hardware, methods, and combinations for coupling blade tracks within gasturbine engines. Further embodiments, forms, features, aspects,benefits, and advantages of the present application shall becomeapparent from the description and figures provided herewith.

BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 depicts an embodiment of a gas turbine engine.

FIG. 2 depicts an embodiment of a blade track assembly.

FIG. 3 depicts an embodiment of a blade track assembly.

FIG. 4 depicts an embodiment of a blade track assembly.

FIG. 5 depicts an embodiment of a blade track.

FIG. 6 depicts an embodiment of a clip.

FIG. 7 depicts an embodiment of a blade track assembly.

FIG. 8 depicts an embodiment of a blade track assembly.

FIG. 9 depicts an embodiment of a blade track.

DETAILED DESCRIPTION OF THE ILLUSTRATIVE EMBODIMENTS

For the purposes of promoting an understanding of the principles of theinvention, reference will now be made to the embodiments illustrated inthe drawings and specific language will be used to describe the same. Itwill nevertheless be understood that no limitation of the scope of theinvention is thereby intended. Any alterations and further modificationsin the described embodiments, and any further applications of theprinciples of the invention as described herein are contemplated aswould normally occur to one skilled in the art to which the inventionrelates.

With reference to FIG. 1, one embodiment of a gas turbine engine 50 isshown. The gas turbine engine includes a compressor 52, combustor 54,and turbine 56 which operate together to provide power. In one form thegas turbine engine 50 is operable to provide power to an aircraft. Asused herein, the term “aircraft” includes, but is not limited to,helicopters, airplanes, unmanned space vehicles, fixed wing vehicles,variable wing vehicles, rotary wing vehicles, unmanned combat aerialvehicles, tailless aircraft, hover crafts, and other airborne and/orextraterrestrial (spacecraft) vehicles. Further, the present inventionsare contemplated for utilization in other applications that may not becoupled with an aircraft such as, for example, industrial applications,power generation, pumping sets, naval propulsion, weapon systems,security systems, perimeter defense/security systems, and the like knownto one of ordinary skill in the art.

The gas turbine engine 50 can take a variety of forms in differentembodiments. Though depicted as a single spool engine in the illustratedembodiment, in other forms the gas turbine engine 50 can include anynumber of other spools. The gas turbine engine 50 can be configured asan adaptive cycle and/or variable cycle engine and furthermore can takethe form of a turbofan, turbojet, turboprop, or turboshaft engine. Othervariations and/or combinations are also contemplated herein.

The gas turbine engine 50 includes turbomachinery components such as thecompressor 52 and turbine 56 which each include rotating features suchas one or more rows of rotating blades. In some forms the turbomachinerycomponents can also include relatively stationary features such as a rowof stator vanes, which can either be fixed in place or of the variablekind. The turbomachinery components can include other features as well.The rotating blades of the turbomachinery components can have a bladetrack (discussed further below) that is located radially outward of therotating blades and which can be used to form a flow path for workingfluid through the turbomachinery components. In one form the bladetracks provide a surface over which the working fluid flows as the fluidreacts with the rotating blades.

Turning now to FIGS. 2 and 3, one embodiment of a blade track assembly58 is disclosed. The blade track assembly 58 includes a blade track 60extending between hangers 62 and 63. The blade track 60 includes aforward end 64 and aft end 66 and which takes on the form of a generallyannular shape that in various embodiments can be either an integralconstruction or composed of a variety of blade track segments thattogether form an annular shape. The illustration in FIG. 2 depicts acircumferential portion of the blade track 60 which can be taken torepresent either a segment of the blade track 60 or a limited view of anannular blade track 60. The forward end 64 and aft end 66 generallyextend circumferentially to form in whole or in part the annular shapeof a completed blade track. The forward end 64 and aft end 66 of theblade track 60 are depicted in the illustrated embodiment as beingreceived within respective openings of the forward hanger 62 and afthanger 63. Either or both ends 64 and 66 can project axially from theblade track 60 along the circumferential length of the blade track 60.Not all forms of the blade track 60, however, need include ends 64 and66 that project axially. Either or both the ends 64 and 66 can becontinuous along the length of the blade track 60, but in someembodiments the blade track 60 can include any number of ends 64 and/or66.

In the illustrated embodiment the blade track 60 includes a layeredconstruction but not all embodiments need include multiple layers. Notall embodiments, however, need be layered. The blade track 60 of theillustrated embodiment includes a backing 68 and an outer surface 70which can be coupled together in a variety of manners. In one form theblade track 60 includes a ceramic material, such as a ceramic matrixcomposite. To set forth just a few non-limiting examples, in the layeredarrangement of the illustrated embodiment the outer surface 70 can be aceramic matrix composite, and in another example the backing 68 is aceramic matrix composite and the reference numeral 70 indicates acoating applied/affixed/etc to the ceramic matrix composite 68.References to the numeral 68 as the backing and to numeral 70 as theceramic matrix composite will be understood as being made of convenienceonly and no limitation is hereby intended regarding the precise form ofeither 68 or 70 unless stated explicitly to the contrary.

Though the backing 68 and the outer surface 70 are shown havinggenerally the same shape, the shapes and/or thicknesses of either orboth the backing 68 and outer surface 70 can be different than thatwhich is depicted. The outer surface 70 is shown as extending along aportion of the backing 68, but in some embodiments the outer surface 70can extend along the entirety of the backing 68. Other variations of theblade track 60 are contemplated herein.

The forward hanger 62 and aft hanger 63 are depicted in the illustratedembodiment as having differentconfigurations/geometries/attachments/etc, but not all embodiments needbe different. The forward hanger 62 and aft hanger 63 of the illustratedembodiment include different radial dimensions such that the forwardhanger 62 is relatively radially smaller than the aft hanger 63 such asmight be expected when the blade track assembly 58 is used within aturbine section of the gas turbine engine 50. The forward hanger 62 andaft hanger 63 of the illustrated embodiment also include differentmechanisms though which they are secured within the gas turbine engine50. The forward hanger 62 includes an opening 72 through which arelatively static structure (shown best in FIG. 3) of the gas turbineengine 50 can be coupled. As used herein the term “static” refers to anysuitable component that is not configured to move in an appreciablesense such as with the rotating shaft of the gas turbine engine. Motionssuch as from thermal expansion/contraction or movement such as acomponent under load can fall within the meaning of the term static. Theopening 72 is shown having a radially upper side, radially lower side,and a backstop and can be referred to as a u-shape. In some applicationsthe opening 72 can be used to slidingly couple with the relativelystatic structure of the gas turbine engine 50. Furthermore, the opening72 can be configured such that it snap-fits to the relatively staticstructure. Other fastening techniques are contemplated herein. Not allembodiments need include the same layout as the opening 72 depicted inthe illustrated embodiment. In some embodiments the forward hanger 62can incorporate an anti-movement feature that cooperates with ananti-movement feature of the relatively static structure of the gasturbine engine 50. For example, the hanger 62 can include a slot thatmates with a pin that extends from and/or is coupled with the relativelystatic structure of the gas turbine engine 50. Other anti-movementfeatures are contemplated herein.

The aft hanger 63 of the illustrated embodiment includes a protrusion 74which is used to couple to the gas turbine engine 50 and secure the afthanger 63 in place. The protrusion 74 can be a flange that is receivedwithin a corresponding opening or against a corresponding surface of thegas turbine engine 50. The protrusion 74 can extend circumferentiallyand radially as depicted, but other variations are also contemplated. Toset forth just one non-limiting example, the protrusion 74 can extendaxially. The protrusion 74 can be any length and need not be continuousalong the length of the aft hanger 63. In some forms the aft hanger 63can be secured to a relatively static portion of the gas turbine engine50 via one or more pins. For example, a pin can extend from therelatively static structure of the gas turbine engine 50 and through anopening of the protrusion 74 to discourage relative movement between thetwo. Other forms of anti-movement features are contemplated herein.

Either or both the forward hanger 62 and aft hanger 63 can includeadditional and/or alternative anti-movement features that are located atsplit lines between adjacent segmented blade tracks 60. In some formsthe anti-movement features can be used to discourage relative movementof blade tracks 60. Alternatively and/or additionally, the anti-movementfeatures can be used to assist in aligning or maintaining position ofthe blade tracks 60 relative to each other and/or relative to thehangers 62 and 63. For example, in one non-limiting embodiment either orboth of the hangers 62 and 63 can include dimples that line up betweenthe split lines of the blade tracks 60. An edge of the blade track 60can engage the dimple to, for example, circumferentially locate theblade track 60. In some forms the anti-movement features can be used toensure a spacing between neighboring blade tracks 60. In anothernon-limiting embodiment the anti-movement feature can be a pin. Othervariations are also contemplated herein.

The openings 76 and 78 in the forward hanger 62 and aft hanger 63,respectively, through which the blade track 60 is received can havedifferent shapes/sizes/geometries/etc, but some embodiments need not bedifferent. For example, the distance between the radially inner portionand radially outer portion of the opening 76 can be different than thedistance between the radially inner portion and radially outer portionof the opening 78. The depth of each opening 76 and 78 can likewise bedifferent in some embodiments, but other embodiments need not bedifferent. The openings 76 and 78 of the illustrated embodiment aregenerally u-shaped having a radially inner and outer portion along witha backstop, but other embodiments can include different shapes. Theopenings 76 and 78 are generally structured to slidingly receive theforward end 64 and aft end 66 of the blade track 60.

In one non-limiting embodiment of the blade track assembly 58, clips 80a and 80 b are used to couple the blade track 60 to the forward hanger62 and aft hanger 63, respectively. Although the illustrated embodimentdepicts clips 80 a and 80 b used in both, some embodiments may notinclude clips 80 a and 80 b in either or both forward hanger 62 and afthanger 63. In one form the clips 80 a and 80 b are capable of flexing inresponse to a stress, for example when the blade track 60 is coupledwith the clips. For example, the clips can have openings 82 a and 82 bthat are sized smaller than a dimension of the blade track 60 such asits thickness. Such capability to flex can be used to provide acompressive holding force to the blade track 60 when it is insertedthrough the openings 82 a and 82 b.

The clips 80 a and 80 b of the illustrated embodiment include roundedbodies 84 a and 84 b extending between ends 86 a/86 b and 88 a/88 b. Therounded bodies 84 a and 84 b can be sized to fit within the openings 76and 78 and in one form are sized to interact in an interference fit. Theround bodies 84 a and 84 b can be flexible such that a fit within theopenings 76 and 78 create a stress to secure the clips 80 a and 80 b.The ends 86 a/86 b and 88 a/88 b of the illustrated embodiment areturned away from the openings 76 and 78, but other forms are alsocontemplated herein.

The clips 80 a and 80 b in the illustrated embodiment extend along anarc corresponding to the openings 76 and 78, and can be an integralannular shape, or segmented, depending on the application. In someembodiments the clips 80 a and 80 b can correspond to the length of asegmented blade track 60, but some embodiments can have differentlengths. If segmented, the clips 80 a and 80 b can be placed within anopening 76 or 78 of a segmented blade track 60, or can span a split linebetween two or more adjacent blade tracks 60. Furthermore, in thoseembodiments having segmented clips 80 a and 80 b, not all segments needhave the same configuration and/or shape. Variations other than thosedepicted or discussed are contemplated herein. Though the clips 80 a and80 b are shown as having similar configurations, other embodiments ofthe blade track assembly 58 may include clips having differentconfigurations and sizes, among other possible differences.

Turning now to FIGS. 4 and 5, the hangers 62 and 63 can optionallyinclude anti-movement features that are structured to interact withcorresponding anti-rotation features of the blade track 60 to discouragerelative movement between the two. In the illustrated embodiment thehangers 62 and 63 include anti-movement features 90 a and 90 b in theform of posts that can be used to interact with anti-movement features92 and 94 (shown with respect to a blade track 60 in FIG. 5) in the formof cutouts. Different configurations of anti-movement features on eitheror both the hangers 62 and 63 and the blade track 60 are contemplatedherein. It should be apparent from the illustration of FIG. 4 that aportion of the hanger 63 is not depicted so that a view of theanti-movement feature 90 b can be shown in better detail. One or moreportions of the anti-movement features 90 a and 90 b can take a formsimilar to that of the anti-movement features 92 and 94. In theillustrated embodiment the anti-movement features 90 a and 90 b are inthe form of semi-circular posts that include an extension 96 and a base98. The semi-circular posts can conform in shape to the semi-circularcutout of the blade track 60. The anti-movement features 90 a and 90 bcan be integral with then hangers 62 and 63, or can alternatively bewelded/brazed/attached to the hangers 62 and 63.

Other variations are contemplated herein for the configuration/shape/etcof the anti-movement features of the blade track 60 and hangers 62 and63. Though one embodiment of a segmented blade track 60 is depicted ashaving the anti-movement features 92 and 94 arranged at its corners,some embodiments can include anti-movement features 92 and 94 locatedelsewhere. Furthermore, the blade track 60 can have any number ofanti-rotation features other than the numbers shown in the illustratedembodiment. For example, some embodiments can include anti-rotationfeatures at one or more corners and additional anti-rotation feature(s)located at a position intermediate the corners. Other embodiments of thehangers 62 and 63 can likewise include any number of anti-rotationfeatures and can be situated in a variety of locations. Some forms ofsegmented hangers 62 and 63 can be arranged such that neighboringhangers combine to create an anti-rotation feature that can used todiscourage relative movement with a blade track 60. For example, thesemi-circular embodiment of the anti-rotation feature shown in theillustrated embodiment can be shared between neighboring segmentedhangers such that each contributes a part of the semi-circular shape.Other variations and combinations are contemplated for the anti-rotationfeatures of both blade track 60 and hangers 62 and 63.

In the illustrated embodiment a clip 100 can be used to furtherdiscourage relative movement and/or secure one or more of the bladetrack 60 and hangers 62 and 63. Some embodiments of the blade trackassembly 58 may not include the clip 100. In one form the clip 100 isflexible and can act as a spring to resist relative motions. To setforth just one non-limiting example, the clip 100 can include multipleflexible portions that resist motion in one or more directions. Suchmultiple flexible portions can be separately made and working inconjunction together, whether coupled or not, or can be an integral cliphaving multiple separate portions. In the illustrated embodiment the dip100 is located around the anti-movement feature 90 a and 90 b and islocated between multiple surfaces of the hangers 62 and 63 and bladetrack 60. Specifically the clip 100 is located in the illustratedembodiment between the base 98 and an edge of the blade track 60 and isalso located between the extension 96 and another edge of the bladetrack 60.

FIG. 6 depicts a view of one embodiment of the clip 100. Though the clip100 is shown as semi-circular in shape, other embodiments of the clip100 can have other shapes. In one form the clip includes multipleportions that can be used collectively to discourage movement inmultiple directions as will be described below with regard to theillustrated embodiment. In general, the multiple portions of the clipcan be separate, or can be coupled together in an assembly or as anintegral clip. The clip 100 includes a portion having a raised body 101that can act to discourage relative radial movement between the bladetrack 60 and the hanger 63, another portion located near a cornerbetween the extension 96 and the base 98, and another portion locatedbetween the extension 96 and a surface of the blade track 60 that candiscourage relative circumferential and/or axial movement. The raisedbody 101 that discourages relative radial movement can take on differentforms in other embodiments. The portion located between the extension 96and the surface of the blade track 60 that discourages relativecircumferential and/or axial movement can take on other forms indifferent embodiments. The clip 100 is not limited to an orthogonalcorner between surfaces as depicted but can be used in other settingswhether or not a turn associated with the surfaces is at ninety degrees.

Turning now to FIGS. 7 and 8, one form of the blade track assembly 58includes a rib 102 that extends between the hangers 62 and 63. In oneembodiment the rib 102 is coupled or secured to one or both of thehangers 62 and 63. In one form the rib 102 is made of sheet metal, butother constructions/materials/etc are also contemplated herein. The rib102 can partially extend between the hangers 62 and 63 in someembodiments. In the illustrated embodiment the rib 102 includes abackplate 104 and sides 106, 108 that together form a u-shaped rib 102.The backplate 104 of the illustrated embodiment includes a depressionforming a u-shape, but other embodiments of the backplate 104 can takeon a variety of different forms.

The sides 106 and 108 can be used to engage one or more blade tracks 60forming a seal to discourage a working fluid from flowing between bladetracks 60. For example, in one non-limiting embodiment the rib 102 canstraddle a split line between segmented blade tracks 60 such that eachside 106 and 108 engages different blade tracks 60. FIG. 8 shows a viewof the rib 102 oriented to straddle a split line between neighboringblade tracks 60, although only one blade track is illustrated for easeof viewing. The sides 106 and 108 can have ends that conform to theshape of the blade track 60, although in some embodiments the ends ofthe sides 106 and 108 need not conform to the blade track 60 at portionsor along the entire dimension of the blade track 60.

FIGS. 7 and 8 also illustrate yet further embodiments of the hangers 62and 63. For example, hanger 62 in the illustrated embodiment depicts ascalloped edge 109 in one portion of the hanger 62 that forms theopening 72. The scalloped edge can be used to interact withcorresponding features in a static structure of the gas turbine engine50 to place the hanger in position and/or further secure it, among otherpossible reasons. The protrusion 74 of hanger 63 is also arranged as yetanother embodiment that includes an axial extension.

In an embodiment depicted in FIG. 9, a blade track 60 can be configuredto include a raised portion 110 that engages with the rib 102 (shown inFIGS. 7 and 8). In one non-limiting form the raised portion 110 canengage one of the sides 106 and 108 substantially along the dimension ofthe blade track 60 to discourage a working fluid from moving through asplit line 112 between adjacent blade tracks 60 and dispersing on theback side of the blade tracks 60. The raised portion 110 can be anyheight difference as measured from a reference point. For example,though an edge of the blade track 60 is shown as raised relative to amiddle portion of the blade track segment, some embodiments may includea middle portion that is raised relative to an and portion of the blade.The end portion can be, for example, stepped down from the middleportion of the blade track segment 60. The raised portion 110 caninclude a stepped portion that interacts with the rib 102 on its lateralside, or the apex of the raised portion 110 can interact directly withthe rib 102. Other variations of a raised seal arrangement arecontemplated.

Any of the features of the embodiments described above can be combinedwith each other to create any number of various embodiments. For examplesome forms of the blade track assembly 58 can include hangers 62 and 63without dimples on split lines between blade tracks 60, but include theclip 100 and anti-movement features to secure the one or more hangers toa static structure of the gas turbine engine 50. In another non-limitingexample, a rib 102 can be used in some blade track assemblies 58 alongwith a clip 80 a and anti-movement feature 90 b. In some embodiments theupstream side of the blade track assembly 58 can include similarfeatures as those on the downstream side of the blade track assembly 58,but not all embodiments need do so. Numerous other combinations andvariations are also contemplated.

One aspect of the instant application provides an apparatus comprising agas turbine engine having a blade track that includes a main body andfore and aft edges that extend axially and circumferentially, the bladetrack supported by a gas turbine engine structure having a receivingportion into which the fore and aft edges can be slindingly inserted.

A feature of the present application provides wherein the receivingportion includes a radially inner member and a radially outer member forreceiving into the receiving portion, and wherein the gas turbine enginestructure includes a plurality of hangers having the receiving portion.

Another feature of the present application provides wherein the gasturbine engine blade track includes a plurality of segmented bladetracks.

Yet another feature of the present application provides wherein at leastone of the circumferentially extending fore and aft edges extends asubstantial length of the blade track.

Still another feature of the present application provides wherein thegas turbine engine structure includes a plurality of segmented hangerseach having receiving portion.

Still yet another feature of the present application further includes au-shaped clip structured to grip the blade track and shaped to fitwithin the receiving portion of the gas turbine engine structure.

A further feature of the present application provides wherein the gasturbine engine structure is an intermediate structure having thereceiving portion for receiving one of the fore and aftcircumferentially extending edges and a second receiving portion forreceiving a protrusion of a static structure of the gas turbine engine.

Yet a further feature of the present application provides wherein thereceiving portion includes a radially inner and a radially outer memberthat create a channel for receipt of the blade track, and the secondreceiving portion includes a second radially inner and a second radiallyouter member that create a second channel for receipt of the protrusionof the static structure.

Another aspect of the instant application provides an apparatuscomprising a pair of gas turbine engine blade track coupling membersuseful for securing a blade track at an upstream end and a downstreamend, each of the pair of blade track coupling members having a u-shapedchannels shaped to receive respective ends of the blade track.

A feature of the present application further includes a gas turbineengine having a turbine section in which is disposed the gas turbineengine blade track coupling members, wherein the pair of gas turbineengine blade track coupling members are not identical, and wherein oneof the pair of gas turbine engine blade track coupling members interactswith an anti-rotation member to discourage movement of the gas turbineengine blade track coupling members.

Another feature of the present application provides wherein at least oneof the pair includes a blade track anti-rotation member structured todiscourage circumferential movement of the blade track, and wherein atleast one of the pair includes a coupling member anti-rotation memberstructured to discourage circumferential movement of the at least one ofthe pair of blade track coupling members relative to a static structureof a gas turbine engine.

Yet another feature of the present application provides wherein the gasturbine engine blade track includes a plurality of blade tracks, whereinat least some of the plurality of blade tracks include a cutoutstructured to engage the anti-rotation member, and which furtherincludes a spring clip located between the anti-rotation member and atleast one of the plurality of blade tracks.

Still yet another feature of the present application provides wherein afirst of the pair of a gas turbine engine blade track coupling membersincludes another u-shaped channel, the another u-shaped channel offsetfrom the u-shaped channel and configured to receive a structure of a gasturbine engine configured to locate the first of the pair within theengine.

A further feature of the present application provides wherein a first ofthe pair of a gas turbine engine blade track coupling members includesan extension structured to be slidingly engaged with a static structureof a gas turbine engine.

A still further feature of the present application further includes aclip inserted into one of the u-shaped channels and having an opening toreceive one of the upstream end and downstream end of the blade track,and wherein the pair of coupling members include an alignment feature tocircumferentially locate a blade track.

Yet still a further feature of the present application provides whereinthe pair of gas turbine engine blade track coupling members includes amember extending axially to couple the pair together.

Yet another aspect of the instant application provides an apparatuscomprising a flexible gas turbine engine clip having an opening disposedbetween a top end and a bottom end of a curvilinear clip body operableto flex when an blade track is inserted through the opening, the engineclip extending in an arc and structured to fit within acircumferentially extending slot of a gas turbine engine staticstructure.

A feature of the present application provides wherein the engine clip isconstructed to withstand relatively elevated temperatures within aturbine section of a gas turbine engine.

Another feature of the present application provides wherein the top endis disposed in a top flared portion of the clip that is configured toturn away from the opening.

Yet another feature of present application provides wherein the topflared portion engages the blade track when installed and a flexiblenature of the clip creates a compressive holding force with the bladetrack.

Still yet another feature of the present application further includes agas turbine engine having a plurality of the flexible gas turbine engineclips arranged in the circumferentially extending slot around an annulusof turbine section of a gas turbine engine.

Yet still another feature of the present application further includes aplurality of segmented blade tracks having a coupling portion engagedwith the plurality of the flexible gas turbine engine clips.

A further feature of the present application provides wherein a topflared portion of the gas turbine engine clip compressingly engages asurface of the circumferentially extending slot of a gas turbine enginestatic structure.

Still yet another aspect of the instant application provides anapparatus comprising a gas turbine engine blade track retention devicein a form of an arcuate corner spring having a material selected tooperate in a gas turbine engine environment and including a curvilinearshape with a first compressive portion and a second compressive portion,the first compressive portion operable to compress in a first directionand the second compression portion operable to compress in a seconddirection, the gas turbine engine blade track retention device operableto discourage movement of a blade track relative to a gas turbine engineby operation of a compressive nature of the first compressive portionand second compressive portion.

A feature of the present application provides wherein the arcuate cornerspring extends in a semi-circular shape and the blade track is a turbineblade track.

Another feature of the present application provides wherein the secondcompressive portion of the arcuate corner spring includes a roundedshape.

Yet another feature of the present application provides wherein therounded shape includes a first rounded portion and a second roundedportion, the first rounded portion configured to engage a staticstructure of the gas turbine engine and the second rounded portionconfigured to engage the blade track, and wherein the material isselected to operate in a turbine section of the gas turbine engine.

Still yet another feature of the present application further includes agas turbine engine having a blade track, the blade track including aportion operable to engage with a static structure of the gas turbineengine, the arcuate corner spring disposed between the static structureand the blade track.

A further feature of the present application provides wherein thearcuate corner spring discourages air flow between the components byproviding sealing contacts on both the static structure and the bladetrack.

A still further feature of the present application provides whereinarcuate corner spring provides two sealing contacts on both the staticstructure and the blade track.

A further aspect of the instant application provides an apparatuscomprising a gas turbine engine blade track segment circumferentiallyextending between a first arc end and a second arc end and having aradially inner side and a radially outer side, the radially outer sidehaving a raised seal portion disposed near the first arc end of theblade track segment and structured to engage a sealing member todiscourage passage of a working fluid between the inner side and theouter side.

A feature of the present application provides wherein the raised sealportion extends to the first arc end of the blade track segment.

Another feature of the present application provides wherein the raisedseal portion includes a face having a surface operable to engage thesealing member.

Still another feature of the present application provides wherein thegas turbine engine blade track segment includes another raised sealportion the second arc end of the blade track segment.

Yet still another feature of the present application provides whereinthe raised seal portion and the another raised seal portion are mirroropposites.

A further feature of the present application includes a gas turbineengine having a plurality of the gas turbine engine blade track segmentsaround a turbine section of the gas turbine engine.

A still further feature of the present application provides wherein asplit line between neighboring blade track segments is sealed with amember that engages raised seal portions on each of the blade tracksegments.

Still a further aspect of the instant application provides an apparatuscomprising a gas turbine engine having a blade track that includes aplurality of segmented track members at least some of which have a sealsurface formed in a surface of the segmented track members opposite froma flow path side of the segmented track members, a first and secondcoupling component structured to support at least two of the segmentedtrack members, and a seal forming member extending from the first andsecond coupling components and configured to engage the seal surface ofthe segmented track members.

A feature of the present application provides wherein the first couplingcomponent includes a plurality of segmented first coupling components.

Another feature of the present application provides wherein the sealforming member extends between the first and second coupling components.

Still another feature of the present application provides wherein theseal forming member is sheet metal, and wherein at least one of thefirst and second coupling components includes an alignment featureuseful to circumferentially position a segmented track member.

Yet still another feature of the present application provides whereineach of the plurality of segmented track members includes a sealsurface.

A further feature of the present application provides wherein each ofthe plurality of segmented track members includes a plurality of sealsurfaces.

A still further feature of the present application further include aplurality of seal forming members useful at the split line between twosegmented track members, wherein lateral edges of the seal formingmembers engage a circumferential edges of the seal surfaces.

A further feature of the present application provides wherein the bladetrack includes a layered construction including an outer constructionand a backing. At least one of the outer construction and the backing isa ceramic matrix composite.

A further feature of the present application provides a method ofassembling a blade track assembly. The method includes securing a bladetrack at an upstream end and a downstream end into a pair of gas turbineengine blade track coupling members of a gas turbine engine. Each of thepair of blade track coupling members have a circumferentially extendingchannel shaped to receive the respective upstream and downstream ends ofthe blade track. The method further includes inserting a flexible gasturbine engine clip extending in an arc within one of thecircumferentially extending channels and inserting one of the upstreamend and downstream end of the blade track through an opening in theengine clip. The opening is disposed between a top end and a bottom endof a curvilinear clip body operable to flex when the blade track isinserted through the opening.

While the invention has been illustrated and described in detail in thedrawings and foregoing description, the same is to be considered asillustrative and not restrictive in character, it being understood thatonly the preferred embodiments have been shown and described and thatall changes and modifications that come within the spirit of theinventions are desired to be protected. It should be understood thatwhile the use of words such as preferable, preferably, preferred or morepreferred utilized in the description above indicate that the feature sodescribed may be more desirable, it nonetheless may not be necessary andembodiments lacking the same may be contemplated as within the scope ofthe invention, the scope being defined by the claims that follow. Inreading the claims, it is intended that when words such as “a,” “an,”“at least one,” or “at least one portion” are used there is no intentionto limit the claim to only one item unless specifically stated to thecontrary in the claim. When the language “at least a portion” and/or “aportion” is used the item can include a portion and/or the entire itemunless specifically stated to the contrary.

What is claimed is:
 1. An apparatus comprising: a gas turbine enginehaving a pair of gas turbine engine blade track coupling members usefulfor securing a blade track at an upstream end and a downstream end, eachof the pair of blade track coupling members having a circumferentiallyextending channel shaped to receive the respective upstream anddownstream ends of the blade track, a flexible gas turbine engine clipextending in an arc and structured to fit within one of thecircumferentially extending channels, the engine clip having an openingto receive one of the upstream end and downstream end of the bladetrack, the opening being disposed between a top end and a bottom end ofa curvilinear clip body operable to flex when the blade track isinserted through the opening, wherein at least one of the pair includesa blade track anti-rotation member structured to discouragecircumferential movement of the blade track, and wherein at least one ofthe pair includes a coupling member anti-rotation member structured todiscourage circumferential movement of the at least one of the pair ofblade track coupling members relative to a static structure of the gasturbine engine; and wherein the gas turbine engine blade track includesa plurality of blade tracks, wherein at least some of the plurality ofblade tracks include a cutout structured to engage the blade trackanti-rotation member, and which further includes a spring clip locatedbetween the blade track anti-rotation member and at least one of theplurality of blade tracks.
 2. The apparatus of claim 1, which furtherincludes a turbine section in which is disposed the gas turbine engineblade track coupling members, wherein the pair of gas turbine engineblade track coupling members are not identical, and wherein at least oneof the pair of gas turbine engine blade track coupling members interactswith a plurality of anti-rotation members to discourage movement of thegas turbine engine blade track coupling members.
 3. The apparatus ofclaim 1, wherein each of the circumferentially extending channelsincludes a radially inner member and a radially outer member forreceiving the upstream end and downstream end into the respectivechannels, and wherein the blade track coupling members include aplurality of hangers having the circumferentially extending channels;and wherein the blade track includes a plurality of segmented bladetracks; and wherein the blade track coupling members include a pluralityof segmented hangers each having the circumferentially extendingchannels.
 4. The apparatus of claim 1, wherein the engine clip isconstructed to withstand relatively elevated temperatures within aturbine section of the gas turbine engine.
 5. The apparatus of claim 1,wherein the top end is disposed in a top flared portion of the clip thatis configured to turn away from the opening; and wherein the top flaredportion engages the blade track when installed and a flexible nature ofthe clip creates a compressive holding force with the blade track. 6.The apparatus of claim 1, which further includes a plurality of theflexible gas turbine engine clips arranged in the circumferentiallyextending slot around an annulus of a turbine section of the gas turbineengine; and which further includes a plurality of segmented blade trackshaving a coupling portion engaged with the plurality of the flexible gasturbine engine clips; and wherein a top flared portion of at least oneof the gas turbine engine clips compressingly engages a surface of thecircumferentially extending slot of the gas turbine engine staticstructure.
 7. The apparatus of claim 1, wherein the blade track includesa ceramic matrix composite material.
 8. The apparatus of claim 1,wherein the blade track includes a layered construction including anouter construction and a backing, wherein at least one of the outerconstruction and the backing is a ceramic matrix composite.
 9. A methodof assembling a blade track assembly comprising: securing a blade trackat an upstream end and a downstream end into a pair of gas turbineengine blade track coupling members of a gas turbine engine, whereineach of the pair of blade track coupling members having acircumferentially extending channel shaped to receive the respectiveupstream and downstream ends of the blade track, inserting a flexiblegas turbine engine clip extending in an arc within one of thecircumferentially extending channels, inserting one of the upstream endand downstream end of the blade track through an opening in the engineclip, wherein the opening is disposed between a top end and a bottom endof a curvilinear clip body operable to flex when the blade track isinserted through the opening, wherein at least one of the pair of bladetrack coupling members includes a blade track anti-rotation memberstructured to discourage circumferential movement of the blade track,and wherein at least one of the pair of blade track coupling membersincludes a coupling member anti-rotation member structured to discouragecircumferential movement of the at least one of the pair of blade trackcoupling members relative to a static structure of the gas turbineengine; and wherein the gas turbine engine blade track includes aplurality of blade tracks, wherein at least some of the plurality ofblade tracks include a cutout structured to engage the blade trackanti-rotation member, and which further includes a spring clip locatedbetween the blade track anti-rotation member and at least one of theplurality of blade tracks.
 10. An apparatus comprising: a blade trackassembly including a blade track having an upstream end and a downstreamend, a forward hanger and an aft hanger, each of the forward hanger andaft hanger having circumferentially extending channels that receive therespective upstream and downstream ends of the blade track, at least oneof the forward hanger and aft hanger includes a hanger anti-movementmember structured to discourage movement of the at least one of theforward hanger and aft hanger relative to the blade track, and a springclip engaged with the blade track to discourage movement of the bladetrack relative to the forward hanger and the aft hanger, wherein theblade track includes a blade track anti-movement cutout that receivesthe hanger anti-movement member to discourage movement of the bladetrack relative to the at least one of the forward hanger and the afthanger and the spring clip is located in the blade track anti-movementcutout and arranged around the hanger anti-movement member.
 11. Theapparatus of claim 10, wherein the hanger anti-movement member includesa post having a base and an extension.
 12. The apparatus of claim 11,wherein the spring clip includes a first portion that receives theextension and the first portion extends into the blade trackanti-movement cutout to discourage axial and circumferential movement ofthe blade track relative to the at least one of the forward hanger andthe aft hanger.
 13. The apparatus of claim 12, wherein the spring clipincludes a second portion that extends away from the first portion andthe second portion engages the blade track and the base so that thespring clip is disposed radially between the blade track and the base todiscourage radial movement of the blade track relative to the at leastone of the forward hanger and the aft hanger.
 14. The apparatus of claim10, wherein the blade track assembly includes a first blade track andsecond blade track adjacent the first blade track, the first and secondblade tracks cooperate to form the blade track anti-movement cutout, thehanger anti-movement member includes a post having a base and anextension, and the post is located in the blade track anti-movementcutout.
 15. The apparatus of claim 14, wherein the spring clip issemi-circular, the spring clip includes a first portion and a secondportion, the first portion of the spring clip extends into the badetrack anti-movement cutout to discourage axial and circumferentialmovement of the blade track relative to the at least one of the forwardhanger and the aft hanger, the second portion of the spring clip extendsaway from the first portion and engages the blade track and the base sothat the spring clip is disposed radially between the blade track andthe base and discourages radial movement of the blade track relative tothe at least one of the forward hanger and the aft hanger.
 16. Theapparatus of claim 10, further comprising a flexible gas turbine engineclip extending in an arc and positioned within the circumferentiallyextending channel of one of the forward hanger and the aft hanger andthe flexible gas turbine engine clip formed to include an opening toreceive one of the upstream end and downstream end of the blade track.17. The apparatus of claim 16, wherein the opening formed in theflexible gas turbine engine clip is disposed between a top end and abottom end of the arc, the opening is sized to be smaller than athickness of the blade track when the flexible gas turbine engine clipis unflexed, and the flexible gas turbine engine clip is configured toflex when the blade track extends into the opening.
 18. The apparatus ofclaim 17, wherein the top end of the arc turns radially outward and thebottom end of the arc turns radially inward away from the blade trackand the flexible gas turbine engine clip supports the blade track suchthat the blade track is spaced apart from the one of the forward hangerand the aft hanger.
 19. The apparatus of claim 10, wherein the upstreamend of the blade track is spaced apart radially inward relative to thedownstream end of the blade track.